固体火箭发动机可靠性设计系统的研究与实现  

Research and Realization of the Reliability Design System for Solid Rocket Motor

作　　者：刘飞[1] 张为华 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《航空计算技术》2005年第1期48-50,共3页Aeronautical Computing Technique

基　　金：国防预研基金资助项目(41328010504)

摘　　要：可靠性设计是固体火箭发动机设计中的一项重要工作,但长期以来这些工作主要依靠多个设计人员共同完成。为了实现固体火箭发动机可靠性设计自动化,本文首先结合固体火箭发动机可靠性设计的工程实际,提出了软件系统的主要功能,然后在总结工程实践中常用的可靠性分配、预计、评估等方法的基础上,确定了系统各模块的计算模型,最后采用C++Builder等软件开发工具,开发了固体火箭发动机可靠性设计系统。实践表明,该系统易于操作,便于工程应用。In designing the solid rocket motor (SRM), the reliability design is a important work, but it need some designers to finish it. To realize the automatization of the Reliability Design for SRM, in this paper, firstly the engineering practice of the Reliability Design for SRM is integrated, and the main functions of software system are abstracted. And then, after summarizing the common methods for reliability allocation, reliability prediction, reliability assessment and so on in engineering, the computation models of each system module are established. Lastly, the C++Builder development tools are adopted, the Reliability Design System for SRM is developed. The engineering practice shows: the system is easy to operate and to apply in engineering.

关 键 词：固体火箭发动机 可靠性设计 软件 功能模块 

分 类 号：V4351[航空宇航科学与技术—航空宇航推进理论与工程]